Pilot’s Manual SECTION VI ANTI-ICE & ENVIRONMENTAL TABLE OF CONTENTS Bleed Air Supply .......................................................................................6-1 Bleed Air Switches................................................................................. 6-1 HP Shutoff Valves ..................................................................................6-2 Pylon Overheat.......................................................................................6-2 Tailcone Leak Detection ........................................................................ 6-2 Bleed Air System Schematic (Figure 6-1) ........................................... 6-3 Anti-Ice Systems ........................................................................................ 6-4 Ice Detector System ............................................................................... 6-4 Wing Inspection Light........................................................................... 6-5 Engine and Nacelle Inlet Anti-Ice ....................................................... 6-5 Wing/Stab Anti-Ice System.................................................................. 6-6 Wing/Stab Anti-Ice System Schematic (Figure 6-2) .........................6-9 Windshield Defog and Ice Protection ............................................... 6-10 Windshield Anti-Ice Schematic (Figure 6-3) .................................... 6-11 Baggage Compartment Heating System.............................................. 6-12 Environmental Control System (ECS) .................................................. 6-13 ECS Controller...................................................................................... 6-13 ECS Shutoff Valve ................................................................................ 6-13 Environmental Control Unit (ECU) or Pack .................................... 6-13 Precooler and Heat Exchangers.................................................... 6-13 Air Cycle Machine (ACM)............................................................. 6-14 ACM Bypass Valve ......................................................................... 6-14 Low Limit Temperature Sensor .................................................... 6-14 Pack Overtemp Sensor................................................................... 6-14 Air Cycle Machine Controls.......................................................... 6-15 Air Cycle Machine System Schematic (Figure 6-4) ......................... 6-15 Temperature Control System ............................................................. 6-16 Temperature Control Valves.......................................................... 6-17 MANUAL TEMP Switch ............................................................... 6-17 Crew and Cabin COLD-HOT Selectors....................................... 6-17 Temperature Control Schematic (Figure 6-5)................................... 6-18 Air Distribution.................................................................................... 6-19 Cockpit/Cabin Air Distribution Schematic (Figure 6-6)................ 6-20 PM-132A VI-1 Pilot’s Manual TABLE OF CONTENTS (Cont) Oxygen System........................................................................................ 6-21 Oxygen Storage and Pressure Regulation ....................................... 6-21 Oxygen System Cockpit Controls ..................................................... 6-22 Oxygen System Schematic (Figure 6-7)............................................ 6-24 Passenger Masks.................................................................................. 6-25 Passenger Mask (Figure 6-8).............................................................. 6-25 Crew Masks.......................................................................................... 6-26 Crew Masks (EROS) (Figure 6-9) ...................................................... 6-26 Crew Masks (Puritan-Bennett) (Figure 6-10)................................... 6-27 Pressurization System ............................................................................ 6-28 Cabin Pressure Control System (CPCS) ........................................... 6-28 Ground Mode.................................................................................. 6-28 Cabin Pressure Controller (CPC) ................................................. 6-28 Emergency Pressurization.................................................................. 6-29 Pressurization Controls and Indicators............................................ 6-30 Cabin Pressurization Control Display......................................... 6-30 LDG ALT Knob............................................................................... 6-31 MANUAL PRESS Switch and MANUAL Knob........................ 6-31 EMER DEPRESS Switch ................................................................ 6-31 Cabin Pressure Control Diagram (Figure 6-11)............................... 6-32 Pressurization Warning System ........................................................ 6-33 VI-2 PM-132A Pilot’s Manual SECTION VI ANTI-ICE & ENVIRONMENTAL BLEED AIR SUPPLY Engine bleed air is used extensively for anti-icing and cabin environ- mental control. The source of this air is through high- and low-pressure ports on each engine compressor. High-pressure (HP) or Low-pressure (LP) air is automatically supplied on an as-needed basis to meet pres- surization requirements. The bleed air obtained from the engine’s HP and LP ports is routed through shutoff and regulator valves. The bleed air is then ducted into either the anti-ice system or the Environmental Control Unit (ECU) or PACK. The PACK conditions the air for the cabin and cockpit distribution systems. Shutoff valves and check valves are installed in the tailcone plumbing to control the bleed air from the left and right engines. In addition to the plumbing, the system includes control switches and incorporates an overheat, overpressurization and leak detection/warning system. A small amount of high-pressure bleed air is also used to pressurize the hydraulic reservoir described in Section 3, this manual. BLEED AIR SWITCHES The L and R BLEED, and EMER PRESS switches, located on the PRES- SURIZATION panel, control the respective left and right bleed-air shutoff valves, and the left and right emergency pressurization valves. The EMER PRESS switch is dependent on the L and R BLEED switches. Both L and R BLEED switches must be in the On position (OFF not il- luminated) in order for both emergency pressurization valves to open with activation of the EMER PRESS switch. However, in the event of a L or R BLEED circuit breaker failure, it is possible to have bleed air sup- plied through an emergency pressurization valve of one engine and through the normal ducting of the other engine. PM-132A 6-1 Pilot’s Manual HP SHUTOFF VALVES A pressure sensor within the HP ducting sends a signal to the ECS con- troller which drives the HP shutoff valves according to altitude and thrust lever angle. The following CAS illumination is specific to the HP shutoff valves: CAS Color Description BLEED OVHT Amber Bleed air temperature in the associated (L or R) bleed air duct is excessive. PYLON OVERHEAT Four temperature sensors around the pylon structure provide for over- heat indication. The following CAS illumination is specific to pylon overheat detection: CAS Color Description ENG PYLON OVHT Red The associated (L or R) engine pylon area is overheated. TAILCONE LEAK DETECTION Tailcone sensing elements are installed along the ducting between the left and right high-pressure shutoff valves including the pack bi-level pressure shutoff valve, ECS pressure valves and ECS check valves. The loop-type elements detect elevated tailcone temperatures caused by a leak in the bleed-air ducting. If a leak occurs between the high-pressure shutoff valve and the ECS check valve, the corresponding BLEED AIR LEAK red CAS and CWP will illuminate. This CAS will also occur if a leak is detected between the ECS check valve and the pack bi-level pressure shutoff valve. The tailcone overheat detection system operates on 28-vdc supplied from the left essential bus. The following CAS illumination is specific to tailcone overheat detection: CAS Color Description BLEED AIR LEAK Red A leak is detected in the associated (L or R) bleed air ducting (tailcone). 6-2 PM-132A Pilot’s Manual HP BLEED PORTS RIGHT ENGINE LP BLEED PORT NAC A/I VALVE HP SOV R BLEED EMER PRESS VALVE 28 VDC ECS CONTROLLER ECS SOV CPCS WING STAB ANTI-ICE ANTI-ICE COCKPIT PACK BI-LEVEL PRSOV RIGHT RH CABIN CH AMC A/I PACK CONTROLLER LEFT CH LH CABIN WING/STAB OFF ON COCKIPT/ HI FLOW CABIN GASPERS ON EMER ON PRESS 28 VDC L BLEED EMER PRESS VALVE OFF OFF HP SOV R BLEED L BLEED NAC A/I VALVE LP BLEED PORT LEFT ENGINE HP BLEED PORTS LEGEND EICAS MESSAGES HP BLEED AIR LP BLEED AIR 1. L BLEED OVHT 2. R BLEED OVHT HP/LP BLEED AIR 3. PACK HIGH FLOW CONDITIONED AIR 4. L EMER PRESS 5. R EMER PRESS VALVE 6. L PYLON OVHT CHECK VALVE 7. R PYLON OVHT TEMP/PRESS SENSOR ELECTRICAL F 40-060000-001-01 BLEED AIR SYSTEM SCHEMATIC Figure 6-1 PM-132A 6-3 Pilot’s Manual ANTI-ICE SYSTEMS Aircraft anti-ice protection is provided through the use of electrically heated and engine bleed air heated anti-ice systems. Electrically heated systems include the pitot-static probes, total air temperature probe, en- gine inlet air temperature/pressure sensors, stall warning vanes, and windshields. Engine bleed air is utilized to provide anti-icing for the leading edge